Transition gauge for electric aircraft

Abstract

In an aspect, a propulsor gauge is provide that provides guidance during a transition of a mode of operation of an electric aircraft. Propulsor gauge may include a processor configured to identify a current thrust envelope parameter of one or more propulsors of electric aircraft. Processor may also determine a recommended range as a function of the propulsor parameter, where the recommended range includes a lower threshold and an upper threshold. The recommended range and thrust envelope parameter may then be shown on a display of propulsor gauge, where a measurement of current thrust envelope parameter relative to recommended range may be represented by an indicator.

What is claimed is: 
     
       1. An electric aircraft, comprising:
 a propulsor; 
 a pilot control configured to control the propulsor based at least in part on a position of the pilot control; 
 a sensor configured to determine condition data of the electric aircraft; 
 a propulsor gauge configured to: 
 determine a thrust envelope parameter of a propulsor of the electric aircraft, wherein the thrust envelope parameter is associated with a transition phase of flight, the transition phase of flight is a transition between a hover flight state and a fixed-wing flight state of the electric aircraft, the thrust envelope parameter comprises a lower threshold and an upper threshold; 
 determine the lower threshold based at least in part on the condition data; and 
 detect a change in the position of the pilot control; and 
 a display configured to: 
 display a visual representation of the thrust envelope parameter; and 
 update the visual representation of the thrust envelope parameter based at least in part on the change in the position of the pilot control. 
 
     
     
       2. The electric aircraft of  claim 1 , wherein the propulsor gauge is further configured to determine the lower threshold based at least in part on one or more of a velocity of the electric aircraft, a rotational velocity of the propulsor, or an angle of attack of the electric aircraft. 
     
     
       3. The electric aircraft of  claim 1 , wherein the propulsor gauge is further configured to determine the upper threshold based at least in part on the condition data. 
     
     
       4. The electric aircraft of  claim 1 , wherein the propulsor is a lift propulsor. 
     
     
       5. The electric aircraft of  claim 1 , wherein the thrust envelope parameter in indicates one or more of:
 a rotational speed of the propulsor, 
 revolutions per minute of the propulsor, 
 a thrust of the propulsor, a torque of the propulsor, 
 power consumption of the propulsor, 
 an angle of the propulsor, 
 a tilt of the propulsor, 
 a current at a motor of the propulsor, or 
 a voltage at a motor of the propulsor. 
 
     
     
       6. The electric aircraft of  claim 1 , wherein the thrust envelope parameter in indicates one or more of:
 an angle of attack, 
 a climb rate, 
 an angular velocity, or 
 an aircraft limitation. 
 
     
     
       7. The electric aircraft of  claim 1 , wherein the thrust envelope parameter in indicates the position of the pilot control. 
     
     
       8. The electric aircraft of  claim 1 , wherein the visual representation comprises a band, wherein the band comprises an upper bound indicating the upper threshold and a lower bound indicating the lower threshold wherein the visual representation. 
     
     
       9. The electric aircraft of  claim 1 , wherein the propulsor gauge is further configured to:
 identify an updated thrust envelope parameter; and 
 determine at least one of an updated upper threshold or an updated lower threshold based at least in part on the updated thrust envelope parameter. 
 
     
     
       10. The electric aircraft of  claim 1 , wherein the propulsor gauge is further configured to determine the upper threshold based at least in part on one or more of a velocity of the electric aircraft, a rotational velocity of the propulsor, or an angle of attack of the electric aircraft. 
     
     
       11. An electric aircraft, comprising:
 a lift propulsor; 
 a pilot control configured to control the lift propulsor based at least in part on a position of the pilot control; 
 a sensor configured to determine condition data of the electric aircraft; 
 a propulsor gauge configured to: 
 determine a thrust envelope parameter of a propulsor of the electric aircraft, wherein the thrust envelope parameter represents an operating condition of the lift propulsor, and the thrust envelope parameter comprises a lower threshold and an upper threshold; 
 determine at least one of the lower threshold or the upper threshold based at least in part on the condition data; and 
 detect a change in at least one of the position of the pilot control or an operating state of the lift propulsor, wherein the operating state comprises a hover flight state or a fixed-wing flight state; and 
 a display configured to: 
 display a visual representation of the thrust envelope parameter; and 
 update the visual representation of the thrust envelope parameter based at least in part on at least one of the position of the pilot control or the operating state of the lift propulsor. 
 
     
     
       12. The electric aircraft of  claim 11 , wherein the operating condition of the lift propulsor comprises one or more of:
 a rotational speed of the lift propulsor, 
 revolutions per minute of the lift propulsor, 
 a thrust of the lift propulsor, 
 a torque of the lift propulsor, 
 power consumption of the lift propulsor, 
 an angle of the lift propulsor, 
 a tilt of the lift propulsor, 
 a current at a motor of the lift propulsor, or 
 a voltage at a motor of the lift propulsor. 
 
     
     
       13. The electric aircraft of  claim 11 , wherein the thrust envelope parameter is based at least in part on the position of the pilot control. 
     
     
       14. The electric aircraft of  claim 11 , wherein the thrust envelope parameter is based at least in part on one or more of:
 an angle of attack, 
 a climb rate, 
 an angular velocity, or 
 an aircraft limitation. 
 
     
     
       15. The electric aircraft of  claim 11 , wherein the visual representation comprises a band, wherein the band comprises an upper bound indicating the upper threshold and a lower bound indicating the lower threshold. 
     
     
       16. The electric aircraft of  claim 11 , wherein the propulsor gauge is configured to determine the thrust envelope parameter based at least in part on sensor data. 
     
     
       17. The electric aircraft of  claim 16 , wherein the sensor data comprises electrical current data associated with a motor of the lift propulsor. 
     
     
       18. The electric aircraft of  claim 11 , wherein the propulsor gauge is further configured to:
 identify an updated thrust envelope parameter; and 
 determine at least one of an updated upper threshold or an updated lower threshold based at least in part on the updated thrust envelope parameter. 
 
     
     
       19. The electric aircraft of  claim 11 , wherein the visual representation comprises one or more gradations, wherein the one or more gradations comprise a first gradation comprising an optimal zone and a second gradation comprising a buffer zone. 
     
     
       20. The electric aircraft of  claim 11 , further comprising an audio component configured to generate an audible alert based at least in part on detecting a pilot input outside of the thrust envelope parameter.